JP2010043568A - Turbine blade and heat radiation acceleration component of turbine blade trailing edge part - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To improve durability of a turbine blade by improving cooling efficiency of the trailing edge part of the turbine blade while maintaining aerodynamic performance. <P>SOLUTION: This turbine blade is supplied with cooling gas to the inside thereof and can discharge the cooling gas supplied to the inside through a notch part 51e formed at an antinode side of the trailing edge part. The blade includes a heat radiation acceleration means 51g installed at a region R exposed by the notch part 51e. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to a heat dissipation promoting component for a turbine blade and a turbine blade trailing edge, and particularly to a turbine blade suitable for a gas turbine and a heat dissipation promoting component for a turbine blade trailing edge.

Turbine blades included in a turbine are generally exposed to a high-temperature fluid. In particular, the turbine blades included in the gas turbine are exposed to a high-temperature combustion gas discharged from the combustor, and thus are exposed to a very high-temperature environment.
In order to increase the durability of the turbine blades exposed to such a high temperature environment, a cooling gas such as cooling air may be supplied into the turbine blades. By supplying the cooling gas to the inside of the turbine blade in this way, it is possible to suppress the temperature increase of the turbine blade and improve the durability of the turbine blade.

By the way, since the trailing edge of the turbine blade is desired to be thin from the viewpoint of the aerodynamic performance of the turbine, it is often difficult to form a flow path for flowing the cooling gas therein. On the other hand, the trailing edge of the turbine blade is a part that has a high heat transfer rate due to a high flow rate of the high-temperature fluid, is easily heated by the high-temperature fluid, and is desired to be cooled.
For this reason, for example, in Patent Document 1 and Patent Document 2, the rear edge portion is thinned by forming a notch portion on the ventral side of the rear edge portion of the turbine blade, and the ventral side exposed by the notch portion is also disclosed. There has been proposed a method of film cooling the trailing edge by blowing a cooling gas toward the surface.
U.S. Pat. No. 4,303,374 US Pat. No. 4,601,638

However, in the methods proposed in Patent Document 1 and Patent Document 2, it is difficult to sufficiently cool the trailing edge of the turbine blade, and further improvement in cooling efficiency is desired.
On the other hand, although it is conceivable to blow cooling gas also on the back side of the rear edge of the turbine blade, secondary fluid such as cooling air is ejected to the high-speed part (the region where the flow is fast) on the back half of the turbine blade. This is not a practical method because it reduces the aerodynamic performance of the turbine.

  The present invention has been made in view of the above-described problems, and an object of the present invention is to improve the cooling efficiency of the trailing edge of the turbine blade while maintaining the aerodynamic performance, thereby improving the durability of the turbine blade.

  The present invention adopts the following configuration as means for solving the above-described problems.

  1st invention is a turbine blade which can discharge the cooling gas supplied inside through the notch part formed in the ventral side of the back edge part while supplying cooling gas inside, A configuration is adopted in which a heat radiation promoting means is provided in a region exposed by the notch.

  According to a second invention, in the first invention, the heat dissipation accelerating means includes a plurality of pin portions erected on a surface exposed by the notch portion.

  According to a third aspect of the present invention, in the first aspect of the present invention, the heat dissipation promoting means is a plurality of dimple portions formed on a surface exposed by the notch portion.

  According to a fourth invention, in the first invention, the heat dissipation accelerating means is erected on a surface exposed by the notch and extends in a direction perpendicular to the flow direction of the cooling gas. A configuration that is a stepped portion is adopted.

  According to a fifth invention, in the first invention, the heat dissipation accelerating means is a lattice structure fitted to a region exposed by the notch.

  6th invention employ | adopts the structure that the said thermal radiation acceleration | stimulation means can be attached or detached with respect to the area | region exposed by the said notch part in the invention in any one of said 1st-5th.

  A seventh aspect of the invention is a heat dissipation promoting component for the turbine blade trailing edge that promotes heat dissipation at the trailing edge of the turbine blade, wherein the cooling gas supplied to the inside is formed on the ventral side of the trailing edge. It is possible to attach to the region exposed by the notch portion of the turbine blade that can be discharged through the portion, and to promote the heat radiation of the trailing edge portion of the turbine blade.

  In an eighth aspect based on the seventh aspect, the heat dissipation promoting component is a lattice structure.

According to the present invention, the back side of the turbine blade is film-cooled by the heat radiation promoting means or the heat radiation promoting component installed in the region exposed by the notch formed on the ventral side of the rear edge of the turbine blade. Without increasing the heat dissipation efficiency at the rear edge.
Therefore, according to the present invention, it is possible to improve the durability of the turbine blade by improving the cooling efficiency of the trailing edge of the turbine blade while maintaining the aerodynamic performance.

  DESCRIPTION OF EXEMPLARY EMBODIMENTS Hereinafter, an embodiment of a turbine blade and a heat dissipation promoting component for the turbine blade according to the invention will be described with reference to the drawings. In the following drawings, the scale of each member is appropriately changed in order to make each member a recognizable size. Moreover, in the following description, the gas turbine engine provided with the turbine blade which concerns on this invention, and the thermal radiation acceleration | stimulation component of a turbine blade is demonstrated.

(First embodiment)
FIG. 1 is a cross-sectional view showing a schematic configuration of a gas turbine engine in which the turbine blades of the present embodiment are installed.
As shown in this figure, the gas turbine engine 1 includes a fan 2, a compressor 3, a combustor 4, and a turbine 5.

The fan 2, the compressor 3, the combustor 4, and the turbine 5 are sequentially arranged from the upstream side to the downstream side of the air flow.
The fan 2 is disposed in the vicinity of the upstream end in the casing 11 and upstream of the cylindrical partition wall 12 and takes in air A from the outside.
The compressor 3 is disposed in the vicinity of the upstream end in the cylindrical partition wall 12, and takes in and compresses a part of the air A taken in by the fan 2.
The combustor 4 is disposed on the downstream side of the compressor 3 in the cylindrical partition wall 12 and mixes and burns fuel with the air A compressed by the compressor 3 and discharges the combustion gas.
The turbine 5 includes a plurality of turbine blades 51 and is disposed on the downstream side of the combustor 4 in the cylindrical partition wall 12. The turbine 5 drives the fan 2 and the compressor 3 with the combustion gas discharged from the combustor 4. The turbine blade 51 is disposed on the downstream side of the stationary blade 52 which is the turbine blade 51 fixed to the cylindrical partition wall 12 and connected to the fan 2 and the compressor 3 via the shaft 13. It is comprised with the moving blade 53 which is the turbine blade 51 to be performed.

The opening on the upstream side of the casing 11 serves as an air intake 14 for taking in air A.
The opening on the downstream side of the casing 11 is a bypass flow outlet 15 for discharging the bypass flow Y. This bypass flow Y is the air A that has not been taken into the compressor 3 out of the air A taken from the air intake 14.
An opening on the downstream side of the cylindrical partition wall 12 is a core flow outlet 16 for discharging the core flow Z. The core flow Z is exhaust from the turbine 5, that is, the combustion gas.

FIG. 2 is a perspective view of the turbine blade 51 of the present embodiment provided in the turbine 5. FIG. 3 is a cross-sectional view of the turbine blade 51.
As shown in these drawings, the turbine blade 51 is hollow inside, and a plurality of through holes 51b are formed on the ventral side 51a. On the other hand, the through-hole 51b is not formed in the high speed part (mainly the latter half part) which is a region where the flow of the back side 51c of the turbine blade 51 is fast.

A plurality of notches 51e are formed on the ventral side 51a of the rear edge 51d of the turbine blade 51. FIG. 4 is an enlarged perspective view of the vicinity of the notch 51e. As shown in this figure, the trailing edge 51d of the turbine blade 51 is formed such that the notch 51e is formed on the abdominal side 51a, so that the thickness d becomes thinner than the case where the notch 51e is not formed. It is configured.
Further, the turbine blade 51 is formed with a slot 51f, which is a through portion communicating from the inside of the turbine blade 51 to the notch 51e, for each notch 51e.

  And in the turbine blade 51 of this embodiment, the several pin part 51g (heat dissipation promotion means) for promoting the heat dissipation of the rear edge part 51d is installed in the area | region R exposed by the notch part 51e. . Specifically, the pin portion 51g is erected on the surface S exposed by the notch portion 51e, and the height thereof is on the ventral side of the turbine blade 51 when the notch portion 51e is not formed. It is set not to protrude outward from the surface position. In this way, by setting the height of the pin portion 51g, it is possible to suppress a decrease in aerodynamic performance.

In the present embodiment, each pin portion 51 g is formed when the turbine blade 51 is formed, and is integrated with the turbine blade 51. However, each pin part 51g is good also as a structure which forms separately from the turbine blade 51, and can be attached or detached with respect to the turbine blade 51. FIG.
Each pin portion 51g is formed of the same material as the turbine blade 51 when formed when the turbine blade 51 is formed, and is equivalent to the turbine blade 51 when formed separately from the turbine blade 51. Or a material having a higher thermal conductivity than the turbine blade 51.

In addition, cooling air (cooling gas) is supplied to the inside of the turbine blade 51 of the present embodiment via a root portion 51 h of the turbine blade 51.
As the cooling air, for example, a part of the outside air taken into the gas turbine engine 1 by the fan 2 can be used.

  When cooling air is supplied to the inside of the turbine blade 51 of the present embodiment having such a configuration via the root portion 51h, the cooling air cools the entire turbine blade 51 from the inside, and a part thereof is a ventral side. It is discharged through the through hole 51b formed in 51a, and the ventral side 51a of the turbine blade 51 is film-cooled.

  Further, a part of the cooling air supplied to the inside of the turbine blade 51 is discharged from the slot 51f, and the surface S exposed by the notch 51e formed on the ventral side 51a of the rear edge 51d is film-cooled. To do. That is, a part of the cooling air supplied to the inside of the turbine blade 51 is discharged through the notch 51e.

And in the turbine blade 51 of this embodiment, the several pin part 51g is standingly arranged in the surface S exposed by the notch part 51e. For this reason, the apparent surface area of the surface S exposed by the notch 51e is increased, the heat radiation surface of the rear edge 51d is increased, the flow disturbance is promoted, and the high-temperature fluid and the cooling air are mixed and heated. Since the diffusion of the heat is promoted, the heat transfer coefficient also increases. For this reason, the turbine blade 51 of the present embodiment is excellent in the cooling efficiency of the trailing edge portion 51d.
On the other hand, in the turbine blade 51 of the present embodiment, the cooling efficiency of the trailing edge portion 51d is improved without causing cooling air to be jetted to the high speed portion (the region where the flow is fast) on the back side 51c of the turbine blade 51. ing. For this reason, it can prevent that aerodynamic performance falls.

  As described above, according to the turbine blade 51 of the present embodiment, it is possible to improve the cooling efficiency of the trailing edge portion of the turbine blade and improve the durability of the turbine blade while maintaining the aerodynamic performance.

(Second Embodiment)
Next, a second embodiment of the present invention will be described. In the description of the second embodiment, the description of the same parts as in the first embodiment will be omitted or simplified.

  FIG. 5 is an enlarged perspective view of the vicinity of the notch 51e of the turbine blade of the present embodiment. As shown in this figure, the turbine blade of this embodiment has a plurality of dimple portions 51i (heat radiation) on the surface S exposed by the notch portion 51e, instead of the pin portion 51g of the turbine blade of the first embodiment. Promotion means) is formed.

Also in the turbine blade of this embodiment, the apparent surface area of the surface S exposed by the notch portion 51e is increased in the dimple portion 51i, the heat radiation surface of the rear edge portion 51d is increased, and the flow is increased. The heat transfer rate is also increased because the turbulence is promoted and the high-temperature fluid and cooling air are mixed to promote heat diffusion. For this reason, the turbine blade of the present embodiment is excellent in the cooling efficiency of the trailing edge portion 51d.
On the other hand, in the turbine blade of the present embodiment, the cooling efficiency of the trailing edge portion 51d is improved without causing the cooling air to be ejected to the high speed portion (the region where the flow is fast) on the back side 51c of the turbine blade. . For this reason, it can prevent that aerodynamic performance falls.

  As described above, according to the turbine blade of this embodiment, it is possible to improve the cooling efficiency of the trailing edge of the turbine blade while maintaining the aerodynamic performance, thereby improving the durability of the turbine blade.

(Third embodiment)
Next, a third embodiment of the present invention will be described. In the description of the third embodiment, the description of the same parts as those of the first embodiment will be omitted or simplified.

  FIG. 6 is an enlarged perspective view of the vicinity of the notch 51e of the turbine blade of the present embodiment. As shown in this figure, in the turbine blade of this embodiment, instead of the pin portion 51g of the turbine blade of the first embodiment, the surface S exposed by the notch portion 51e has a cooling air flow direction. A plurality of arranged step portions 51j (heat radiation promoting means) are erected.

  These step portions 51j are erected on a surface S that extends in a direction orthogonal to the flow direction of the cooling air and is exposed by the notch portion 51, and the height thereof does not form the notch portion 51e. In this case, it is set so as not to protrude outward from the surface position on the ventral side of the turbine blade. In this way, by setting the height of the stepped portion 51j, it is possible to suppress a decrease in aerodynamic performance.

In the present embodiment, each step portion 51j is formed when the turbine blade is formed, and is integrated with the turbine blade. However, each step portion 51j may be formed separately from the turbine blade and detachable from the turbine blade.
Each step portion 51j is formed of the same material as the turbine blade when it is formed when the turbine blade is formed, and when it is formed separately from the turbine blade, it has the same or high heat as the turbine blade. It is formed of a material having conductivity.

Also in the turbine blade of this embodiment, the apparent surface area of the surface S exposed by the notch 51e is increased at the stepped portion 51j, the heat dissipation surface of the trailing edge portion 51d is increased, and the flow is increased. The heat transfer rate is also increased because the turbulence is promoted and the high-temperature fluid and cooling air are mixed to promote heat diffusion. For this reason, the turbine blade of the present embodiment is excellent in the cooling efficiency of the trailing edge portion 51d.
On the other hand, in the turbine blade of the present embodiment, the cooling efficiency of the trailing edge portion 51d is improved without causing the cooling air to be ejected to the high speed portion (the region where the flow is fast) on the back side 51c of the turbine blade. . For this reason, it can prevent that aerodynamic performance falls.

  As described above, according to the turbine blade of this embodiment, it is possible to improve the cooling efficiency of the trailing edge of the turbine blade while maintaining the aerodynamic performance, thereby improving the durability of the turbine blade.

(Fourth embodiment)
Next, a fourth embodiment of the present invention will be described. In the description of the fourth embodiment, the description of the same parts as those of the first embodiment will be omitted or simplified.

  FIG. 7 is an enlarged perspective view of the vicinity of the notch 51e of the turbine blade of the present embodiment. As shown in this figure, the turbine blade of the present embodiment has a lattice structure that is a heat dissipation promoting component in a region R exposed by the notch 51e, instead of the pin portion 51g of the turbine blade of the first embodiment. The body 100 (heat dissipation promoting means) is fitted.

FIG. 8 is a perspective view of the lattice structure 100. The lattice structure 100 is configured as a separate part that can be attached to the turbine blade, and is formed of a material having the same or high thermal conductivity as the turbine blade.
Further, the lattice structure 100 is set so that its height does not protrude outward from the surface position on the ventral side of the turbine blade when the notch 51e is not formed. Thus, by setting the height of the lattice structure 100, it is possible to suppress a decrease in aerodynamic performance.
Such a lattice structure 100 can be fixed to the turbine blade by a nickel brazing material having high heat resistance, for example, and can be retrofitted to an existing turbine blade having a notch. ing.

And according to the turbine blade of this embodiment having such a lattice structure 100, the apparent surface area of the surface S exposed by the notch 51e is increased in the lattice structure 100, and the trailing edge portion As the heat-dissipating surface of 51d is increased, the turbulence of the flow is promoted, and the high-temperature fluid and the cooling air are mixed to promote the diffusion of heat, so that the heat transfer coefficient is also increased. For this reason, the turbine blade of the present embodiment is excellent in the cooling efficiency of the trailing edge portion 51d.
On the other hand, in the turbine blade of the present embodiment, the cooling efficiency of the trailing edge portion 51d is improved without causing the cooling air to be ejected to the high speed portion (the region where the flow is fast) on the back side 51c of the turbine blade. . For this reason, it can prevent that aerodynamic performance falls.

  As described above, according to the turbine blade of this embodiment, it is possible to improve the cooling efficiency of the trailing edge of the turbine blade while maintaining the aerodynamic performance, thereby improving the durability of the turbine blade.

  Moreover, according to the lattice structure 100 in the present embodiment, it is possible to retrofit an existing turbine blade having a notch. For this reason, it becomes possible to improve the cooling efficiency of the trailing edge portion of the turbine blade and improve the durability of the turbine blade while maintaining the aerodynamic performance of the existing turbine.

  As mentioned above, although preferred embodiment of the heat dissipation acceleration | stimulation component of the turbine blade and turbine blade trailing edge part which concerns on this invention was described referring an accompanying drawing, it cannot be overemphasized that this invention is not limited to the said embodiment. Various shapes, combinations, and the like of the constituent members shown in the above-described embodiments are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

For example, in the said embodiment, the gas turbine engine provided with the turbine blade of this embodiment and the heat dissipation acceleration | stimulation component of a turbine blade was mentioned and demonstrated.
However, the present invention is not limited to this, and it is also possible to use the turbine blade of this embodiment and the heat dissipation promoting component of the turbine blade in a gas turbine or steam turbine for power generation.

Moreover, in the said embodiment, the pin part, the dimple part, the step part, and the grating | lattice structure were mentioned and demonstrated as the thermal radiation promotion means of this invention.
However, the present invention is not limited to this, and as the heat radiation promoting means of the present invention, the apparent area of the surface exposed by the notch is increased, and the turbulence of the flow is promoted to transfer the heat. A structure that also increases the rate can be used. For example, the lattice structure may be a honeycomb structure.

Moreover, in the said embodiment, the structure which the heat dissipation acceleration | stimulation component retrofitted of this invention was a lattice structure was demonstrated.
However, the present invention is not limited to this, and the shape of the heat radiation promoting component of the present invention is arbitrary.
For example, a fin structure including a plurality of fins can be used as the heat dissipation promoting component of the present invention.

  Moreover, in the said embodiment, although the structure which uses external air as a cooling gas was demonstrated, this invention is not limited to this, It is also possible to use other gas as a cooling gas.

It is sectional drawing which shows schematic structure of the gas turbine engine provided with the turbine blade in 1st Embodiment of this invention. It is a perspective view of the turbine blade in a 1st embodiment of the present invention. It is sectional drawing of the turbine blade in 1st Embodiment of this invention. It is the perspective view which expanded the vicinity of the notch part of the turbine blade in 1st Embodiment of this invention. It is the perspective view which expanded the vicinity of the notch part of the turbine blade in 2nd Embodiment of this invention. It is the perspective view which expanded the vicinity of the notch part of the turbine blade in 3rd Embodiment of this invention. It is the perspective view which expanded the vicinity of the notch part of the turbine blade in 4th Embodiment of this invention. It is a perspective view of the lattice structure in a 4th embodiment of the present invention.

Explanation of symbols

  DESCRIPTION OF SYMBOLS 1 ... Gas turbine engine, 5 ... Turbine, 51 ... Turbine blade, 51a ... Abdominal side, 51c ... Back side, 51d ... Rear edge part, 51e ... Notch part, 51g ... Pin part ( Radiating promotion means), 51i... Dimple (radiation promoting means), 51j... Step (heat radiating promotion means), 100... Lattice structure (heat radiating promotion means, radiating promotion parts), R. Exposed area, S ... Surface exposed by notch

Claims (8)

A cooling blade is supplied to the inside, and the cooling gas supplied to the inside can be discharged through a notch formed on the ventral side of the rear edge,
A turbine blade comprising a heat radiation promoting means installed in a region exposed by the notch.   2. The turbine blade according to claim 1, wherein the heat radiation promoting means is a plurality of pin portions standing on a surface exposed by the notch portion.   The turbine blade according to claim 1, wherein the heat radiation promoting means is a plurality of dimple portions formed on a surface exposed by the notch portion.   2. The heat radiation promoting means is a plurality of stepped portions that are erected on a surface exposed by the notch and that extend in a direction perpendicular to the flow direction of the cooling gas. Turbine blades.   2. The turbine blade according to claim 1, wherein the heat radiation promoting means is a lattice structure fitted in a region exposed by the notch.   The turbine blade according to any one of claims 1 to 5, wherein the heat radiation promoting means is detachable from a region exposed by the notch.   The cooling gas supplied to the inside can be attached to a region exposed by the notch of the turbine blade that can be discharged through a notch formed on the ventral side of the rear edge, and A heat radiation promoting component for a trailing edge of a turbine blade, which promotes heat radiation of the trailing edge of the turbine blade. The heat radiation promoting component for a turbine blade trailing edge according to claim 7, wherein the heat radiation promoting component is a lattice structure.

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